FR3057541B1 - INTEGRATED SHOCK ABSORBER WITHIN A ROTOR BLADE - Google Patents

INTEGRATED SHOCK ABSORBER WITHIN A ROTOR BLADE Download PDF

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Publication number
FR3057541B1
FR3057541B1 FR1601495A FR1601495A FR3057541B1 FR 3057541 B1 FR3057541 B1 FR 3057541B1 FR 1601495 A FR1601495 A FR 1601495A FR 1601495 A FR1601495 A FR 1601495A FR 3057541 B1 FR3057541 B1 FR 3057541B1
Authority
FR
France
Prior art keywords
blade
elastomeric material
shock absorber
rotor blade
drag damper
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
FR1601495A
Other languages
French (fr)
Other versions
FR3057541A1 (en
Inventor
Stephane Mazet
Jean Romain Bihel
Sylvain Berthalon
Mathias Fournier
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Helicopters SAS
Original Assignee
Airbus Helicopters SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Helicopters SAS filed Critical Airbus Helicopters SAS
Priority to FR1601495A priority Critical patent/FR3057541B1/en
Priority to EP17194173.5A priority patent/EP3309069B1/en
Priority to PL17194173T priority patent/PL3309069T3/en
Priority to US15/728,750 priority patent/US11142307B2/en
Priority to CN201710942808.5A priority patent/CN107953989B/en
Publication of FR3057541A1 publication Critical patent/FR3057541A1/en
Application granted granted Critical
Publication of FR3057541B1 publication Critical patent/FR3057541B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/51—Damping of blade movements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/001—Vibration damping devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/35—Rotors having elastomeric joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B64C27/48—Root attachment to rotor head

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Vibration Dampers (AREA)

Abstract

La présente invention concerne un amortisseur de traînée (1) agencé à l'intérieur d'une pale (20) d'un rotor d'un aéronef à voilure tournante. Ledit amortisseur de traînée (1) comporte une armature intérieure (3) munie d'une cage dans laquelle est agencée une liaison à rotule, une armature extérieure (4) destinée à être solidarisée à ladite pale (20) et un organe en matériau élastomère (5) agencé entre lesdites deux armatures (3,4). Lesdites deux armatures (3,4) et ledit organe en matériau élastomère (5) s'étendent au-delà de la zone autour de ladite cage afin que des mouvements relatifs entre lesdites deux armatures (3,4) consécutifs aux mouvements de ladite pale (20) soient amortis par des déformations dudit organe en matériau élastomère (5), au moins une partie dudit amortisseur de traînée (1) étant destinée à occuper une partie de l'intérieur de ladite pale (20) traditionnellement remplie de mousse.The present invention relates to a drag damper (1) arranged inside a blade (20) of a rotor of a rotary wing aircraft. Said drag damper (1) comprises an inner armature (3) provided with a cage in which is arranged a ball joint, an outer armature (4) to be secured to said blade (20) and a member of elastomeric material (5) arranged between said two frames (3,4). Said two armatures (3,4) and said elastomeric material member (5) extend beyond the zone around said cage so that relative movements between said two armatures (3,4) consecutive to movements of said blade (20) are damped by deformations of said member elastomeric material (5), at least a portion of said drag damper (1) being intended to occupy a portion of the interior of said blade (20) traditionally filled with foam.

FR1601495A 2016-10-14 2016-10-14 INTEGRATED SHOCK ABSORBER WITHIN A ROTOR BLADE Expired - Fee Related FR3057541B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR1601495A FR3057541B1 (en) 2016-10-14 2016-10-14 INTEGRATED SHOCK ABSORBER WITHIN A ROTOR BLADE
EP17194173.5A EP3309069B1 (en) 2016-10-14 2017-09-29 A lead-lag damper integrated inside a blade of a rotor
PL17194173T PL3309069T3 (en) 2016-10-14 2017-09-29 A lead-lag damper integrated inside a blade of a rotor
US15/728,750 US11142307B2 (en) 2016-10-14 2017-10-10 Lead-lag damper integrated inside a blade of a rotor
CN201710942808.5A CN107953989B (en) 2016-10-14 2017-10-11 Lead-lag damper integrated inside the blades of a rotor

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1601495 2016-10-14
FR1601495A FR3057541B1 (en) 2016-10-14 2016-10-14 INTEGRATED SHOCK ABSORBER WITHIN A ROTOR BLADE

Publications (2)

Publication Number Publication Date
FR3057541A1 FR3057541A1 (en) 2018-04-20
FR3057541B1 true FR3057541B1 (en) 2019-03-29

Family

ID=58314287

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1601495A Expired - Fee Related FR3057541B1 (en) 2016-10-14 2016-10-14 INTEGRATED SHOCK ABSORBER WITHIN A ROTOR BLADE

Country Status (5)

Country Link
US (1) US11142307B2 (en)
EP (1) EP3309069B1 (en)
CN (1) CN107953989B (en)
FR (1) FR3057541B1 (en)
PL (1) PL3309069T3 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12043368B2 (en) 2022-03-23 2024-07-23 General Electric Company Rotating airfoil assembly

Family Cites Families (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2125150B1 (en) 1971-02-15 1973-12-07 Aerospatiale
US3842945A (en) * 1971-05-13 1974-10-22 J Potter Viscoelastic damper
FR2263151B2 (en) * 1974-03-07 1976-10-08 Aerospatiale
FR2305343A2 (en) 1975-03-26 1976-10-22 Aerospatiale ROTOR FOR GIRAVIONS
FR2228663A1 (en) 1973-05-10 1974-12-06 Aerospatiale Rotor for rotating wing aircraft - has yoke connecting rotor arm and star shaped rotor has low weight
GB1539200A (en) * 1976-12-08 1979-01-31 Westland Aircraft Ltd Helicopter rotors
FR2427251A1 (en) 1978-06-02 1979-12-28 Aerospatiale Helicopter rotor with rigid hub - has each blade mounted via laminated spherical bearings and strut
FR2516891A1 (en) * 1981-11-25 1983-05-27 Aerospatiale ROTOR FOR GIRAVIONS, WITH ARTICULATIONS INTEGRATED INTO THE BLADE FOOT
FR2528382A1 (en) * 1982-06-11 1983-12-16 Vibrachoc Sa VIBRATION DAMPER AND IN PARTICULAR FREQUENCY ADAPTER FOR HELICOPTER BLADE
US4427340A (en) * 1982-06-24 1984-01-24 Bell Helicopter Textron Inc. Soft inplane bearingless helicopter rotor
US4676720A (en) * 1984-07-10 1987-06-30 Kawasaki Jukogyo Kabushiki Kaisha Bearingless hub structure for rotary-wing aircrafts
FR2630703B1 (en) 1988-04-29 1990-08-24 Aerospatiale ROTOR HEAD OF A GIRAVION WITH ELASTIC RETURN INTERPAL DRAWERS WITH BUILT-IN DAMPING
JPH085437B2 (en) * 1990-04-27 1996-01-24 防衛庁技術研究本部長 Articulated hub structure for rotorcraft
US5407325A (en) * 1990-09-27 1995-04-18 Societe Nationale Industrielle Et Aerospatiale Rotor head for rotary wing aircraft
FR2680845B1 (en) 1991-09-04 1995-02-10 Vibrachoc Sa VIBRATORY ENERGY ABSORBER.
FR2702733B1 (en) * 1993-03-18 1995-06-16 Eurocopter France ROTOR HEAD FOR GIRAVION.
DE19620427C1 (en) * 1996-05-21 1997-06-12 Eurocopter Deutschland Rotor blade connection for helicopters
ITMI991124A1 (en) 1998-05-28 2000-11-21 Eurocopter Deutschland SHOVEL FOR A ROTOR WITHOUT HELICOPTER SUPPORT
CA2533201C (en) 2003-08-27 2010-06-22 Bell Helicopter Textron Inc. Dual spring rate damper
EP1640266B1 (en) * 2004-09-28 2007-04-18 Agusta S.p.A. Helicopter rotor with a vibration damping device
FR2898581B1 (en) 2006-03-15 2009-01-09 Eurocopter France BLADE COMPRISING AN INTEGRATED CUFF AND ROTOR OF GIRAVION PROVIDED WITH SUCH A BLADE.
WO2009102324A1 (en) 2008-02-12 2009-08-20 Bell Helicopter Textron Inc. Lead-lag damper for rotor hubs
FR2928344B1 (en) 2008-03-06 2011-01-21 Hutchinson DAMPING DEVICE AND AERODYNE ROTOR SYSTEM INCORPORATING IT
FR2929675B1 (en) 2008-04-07 2013-02-22 Eurocopter France IMPROVED VISCOELASTIC DAMPING DEVICE
US8632308B2 (en) * 2008-11-26 2014-01-21 Lord Corporation Fluid elastomeric damper assembly including internal pumping mechanism and volume compensator
WO2010082936A1 (en) 2009-01-19 2010-07-22 Bell Helicopter Textron Inc. Stiff-in-plane rotor configuration
FR2943621B1 (en) 2009-03-27 2011-04-15 Eurocopter France BLADE EQUIPPED WITH A TRAINING DAMPER AND ROTOR PROVIDED WITH SUCH A BLADE
US8827586B2 (en) * 2012-06-27 2014-09-09 The Boeing Company Damping mechanical linkage
US9656747B2 (en) 2013-03-14 2017-05-23 Bell Helicopter Textron Inc. Soft in-plane and stiff out-of-plane rotor system
JP6189673B2 (en) * 2013-08-14 2017-08-30 山下ゴム株式会社 Resin torque rod

Also Published As

Publication number Publication date
PL3309069T3 (en) 2019-09-30
EP3309069B1 (en) 2019-04-17
CN107953989A (en) 2018-04-24
EP3309069A1 (en) 2018-04-18
US11142307B2 (en) 2021-10-12
CN107953989B (en) 2021-03-02
US20180105265A1 (en) 2018-04-19
FR3057541A1 (en) 2018-04-20

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